Experimental study of rotation effect on film cooling over the flat wall with a single hole

Tao, Zhi; Yang, Xiaoguang; Ding, Shuiting; Xu, Guoqiang; Wu, Hongwei; Deng, Hongwu; Luo, Xianwu

doi:10.1016/j.expthermflusci.2007.12.003

Cited by 21 publications

(11 citation statements)

References 20 publications

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“…Significantly, with increasing blowing ratio from BR=1 to 1.5 the effectiveness cooling will be increased by about 20.1% and 15.2% through respective increases in BR to 1.5 and 2 (near the leading edge of blade). The pressure side effectiveness cooling is higher than suction side at this regime (high BR enhanced film cooling on pressure side), a trend in agreement with Burdet and Abhari [7], and Tao et al [13] attributable to the similar angle of injection (45 0 ) and lateral holes inclined (9.13 0 ) design.…”

Section: Boundary Conditionssupporting

confidence: 77%

Numerical simulation of blowing ratio effects on film cooling on a gas turbine blade

Daud¹,

Li²,

Bég³

et al. 2011

Computational Methods and Experimental Measurements XV

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This article investigates the film cooling effectiveness and heat transfer in three regimes for a film-cooled gas turbine blade at the leading edge of the blade with 45 0 angle of injection. A Rolls Royce blade has been used in this study as a solid body with the blade cross section from Hub to Shroud varying with a degree of skewness. A 3-D finite-volume method has been employed (FLUENT 6.3) with a   k turbulence model. The numerical results show the effectiveness cooling and heat transfer behavior with increasing injection blowing ratio BR (1, 1.5 and 2). In terms of the film cooling performance, high BR enhances effectiveness cooling on pressure side and extends the protected area along the spanwise direction from hub to shroud. The influence of increased blade film cooling can be assessed via the values of Nusselt number in terms of reduced heat transfer to the blade.

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Section: Boundary Conditionssupporting

confidence: 77%

Numerical simulation of blowing ratio effects on film cooling on a gas turbine blade

Daud¹,

Li²,

Bég³

et al. 2011

Computational Methods and Experimental Measurements XV

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“…The test rig had a 600 mm rotating radius, and the rotating speed could be up to 3000 rpm, driven by a 30 kW electric motor. It was almost the same as that of Tao et al [20]. The test model was placed in the test section.…”

Section: Introductionmentioning

confidence: 98%

Experiments on impingement heat transfer with film extraction flow on the leading edge of rotating blades

Deng¹,

Gu²,

Zhu³

et al. 2012

International Journal of Heat and Mass Transfer

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“…However, an interesting study was carried out by Tao et al [28] to investigate the rotation effects on film cooling over a flat blade using a liquid-crystal technique. Different rotational speeds ranging from 0 to 1000 rpm were examined.…”

Section: Rotation Effectsmentioning

confidence: 99%

A Numerical Simulation of the Effects of Swirling Flow on Jet Penetration in a Rotating Channel

Al-Zurfi

Turan

2014

Flow Turbulence Combust

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The hydrodynamic effects of a jet in a swirling cross-flow problem, which is related to gas turbine blades film cooling, were numerically simulated using large eddy simulation with artificial inflow boundary conditions. The purpose of this study is to investigate the effects of swirling flow on a jet effusing from an inclined hole in a rotating channel. The finite volume method and the unsteady PISO algorithm were applied on a non-uniform staggered grid. The work is naturally divided into two main parts. The first part (the swirl flow generator), is a channel rotates axially to generate a turbulent swirling flow at different values of swirl number (SN) of 0.0, 0.15, 0.3, and 0.5 while the second part (test section), is a channel rotating about a parallel axis to investigate the interaction of a square jet with the turbulent swirling flow, generated by the first part, for the prediction of the film cooling under rotating conditions. Four different values of rotation number (Ro) were applied to the test section. The air jet was injected at 30 deg in the streamwise direction, at a velocity ratio of 1.0 and a jet Reynolds number of 4,700, based on the hole width and the jet exit velocity. It was found that the swirling flows primarily displayed the velocity profile of a forced vortex. Weak reverse flow was observed near the main vortex core, which moved in the direction of the swirl and deformed the kidney shape of the Counter Rotating Vortex Pair. As SN increases (SN > 0), the jet trajectory twists in an increasingly x-axis direction due to the centrifugal force effects of the swirl flow, and shifts from the centreline of the channel Flow Turbulence Combust to the right-hand side (Z/D = + 1.5). Also, it was shown that rotation has a strong impact on the mixing behaviour and film cooling effectiveness. Finally, it was concluded that the film cooling decreases rapidly as SN increases.

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Experimental study of rotation effect on film cooling over the flat wall with a single hole

Cited by 21 publications

References 20 publications

Numerical simulation of blowing ratio effects on film cooling on a gas turbine blade

Numerical simulation of blowing ratio effects on film cooling on a gas turbine blade

Experiments on impingement heat transfer with film extraction flow on the leading edge of rotating blades

A Numerical Simulation of the Effects of Swirling Flow on Jet Penetration in a Rotating Channel

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